Molded-In Insert and Method for Fiber Reinforced Thermoplastic Composite Structure

ABSTRACT

In an embodiment of the disclosure, there is provided a molded-in insert for high strength retention in a fiber reinforced thermoplastic composite structure. The insert has a cylindrical body and at least one circumferential groove formed in the cylindrical body, the groove having a substantially concave configuration, having a groove radius of 0.025 inch or greater, and having the groove radius greater than or equal to a groove depth.

BACKGROUND

1) Field of the Disclosure

The disclosure relates generally to inserts for use in structures, andmore particularly, to molded-in inserts for use in composite structuresand parts in aircraft, spacecraft, and other vehicles.

2) Description of Related Art

Inserts may be used in the assembly of composite and metal structures orparts for various transport vehicles, such as aircraft, spacecraft,rotorcraft, watercraft, automobiles, trucks, buses, or other transportvehicles. Such inserts may be used to receive mating fasteners, provideattachment points for multi-part assemblies, and provide load transferpoints. Examples of such inserts may include press-fit inserts, swagedinserts, molded-in inserts, threaded inserts, or other suitable insertsor fittings.

Methods for installing inserts into composite and metal structures orparts may include, for example, mold in place methods, such as wheremolded-in inserts are installed during molding, or for example, moreexpensive post-molding methods, such as where press-fit inserts orswaged inserts are installed after molding.

Known press-fit inserts and swaged inserts may be pressed into anopening in metal structures or parts after molding without the use ofspecial tools or fasteners. However, known press-fit inserts and swagedinserts designed for press-fit installation in metal structures or partsmay not work well with fiber reinforced thermoplastic compositestructures or parts due to the non-ductile nature of the fiberreinforced thermoplastic composite material. Such non-ductile fiberreinforced thermoplastic composite material may lead to over-stressingof the material around the insert if the fit is too tight or may lead topoor retention of the insert if the fit is too loose, thus resulting inan improper fit. Thus, a proper fit of such known press-fit and swagedinserts may be difficult to attain with non-ductile materials such asfiber reinforced thermoplastic composite material. Moreover,post-molding methods for installing known press-fit inserts or swagedinserts may incur increased labor and manufacturing costs, increasedset-up and operating time, and increased final part cost.

Known molded-in inserts and threaded inserts may be molded into thecomposite or metal structure or part during molding. For example, FIG.2A is an illustration of a front perspective view of a known molded-ininsert 30 that may be molded in place in injection molded structures orparts. The molded-in insert 30 has knurled surfaces 34 with sharp knurls36 and has a groove 38 with sharp edges 40, sharp internal corners 42,and a small width 44. Further, FIG. 2B is an illustration of a frontperspective view of a known molded-in threaded insert 32 that may bemolded in place in injection molded structures or parts. The molded-inthreaded insert 32 has knurled surfaces 34 with sharp knurls 36, hasgroove 38 with sharp edges 40 and sharp internal corners 42, and smallwidth 44, and has internal threads 46. Such known molded-in insert 30and molded-in threaded insert 32 may use the knurled surfaces 34 and/orgrooves 38 with sharp edges 40, sharp internal corners 42, and smallinternal radii 44 to retain such molded-in insert 30 and molded-inthreaded insert 32 in place in thermoplastic composite parts.

However, such known molded-in insert 30 and molded-in threaded insert 32may not work well with compression molded fiber reinforced thermoplasticcomposite structures or parts due to difficulties in filling the smallradii 44 or the sharp internal corners 42 of the groove 38 during themolding process. FIG. 3 is an illustration of a cross-sectional top viewof the known molded-in insert 30 showing the knurled surface 34 withsharp knurls 36 after being compression molded in place in a carbonfiber reinforced thermoplastic composite part 50 comprised of a carbonfiber reinforced thermoplastic composite material 52 having reinforcingcarbon fibers 54 in a resin matrix 55. The reinforcing carbon fibers 54,in general, do not flow into or enter void areas 56 between the knurls36, and thus, the formation of such void areas 56 of incompleteconsolidation may be promoted within the carbon fiber reinforcedthermoplastic composite material 52, which can undermine retentionstrength of the molded-in insert 30 within the carbon fiber reinforcedthermoplastic composite part 50. Moreover, the reinforcing carbon fibers54 of the carbon fiber reinforced thermoplastic composite material 52may not flow into the small radii 44 (see FIGS. 2A, 2B) and/or sharpinternal corners 42 (see FIGS. 2A, 2B) and may thus limit retentionstrength to the capability of the resin matrix 55 alone, which may berelatively weak.

Further, such known molded-in insert 30 and molded-in threaded insert 32may have sharp edges 40 (see FIG. 4) which may cut reinforcing carbonfibers 54 during the molding process. FIG. 4 is an illustration of across-sectional side view of known molded-in insert 30 showing thegroove 38 with sharp edges 40 and sharp internal corners 42 molded inplace in the carbon fiber reinforced thermoplastic composite part 50comprised of carbon fiber reinforced thermoplastic composite material 52having reinforcing carbon fibers 54 in a resin matrix 55. The pressureson and flow of the carbon fiber reinforced thermoplastic compositematerial 52 during molding may cause the reinforcing carbon fibers 54 tohave difficulty flowing into the sharp internal corners 42, thuscreating void areas 56 of incomplete consolidation. Pressures on andflow of the carbon fiber reinforced thermoplastic composite material 52during molding may cause the reinforcing carbon fibers 54 to be cut orsevered when pressed against the sharp edges 40, such as at locations58. Cut or severed reinforcing carbon fibers 54 may undermine retentionstrength of the molded-in insert 30 within the carbon fiber reinforcedthermoplastic composite part 50.

FIG. 5A is an illustration of a cross-sectional side view showing voidareas 56 of incomplete consolidation where reinforcing carbon fibers 54of carbon fiber reinforced thermoplastic composite material 52 areforced to flow around a relatively sharp edge 60 of a carbon fiberreinforced thermoplastic composite part 62. FIG. 5B is an illustrationof a close-up view of the circled portion 5B of FIG. 5A showing the voidareas 56 of incomplete consolidation. Such void areas 56 of incompleteconsolidation may undermine retention strength of molded-in insertswithin the fiber reinforced thermoplastic composite parts or structures.

Accordingly, there is a need in the art for a molded-in insert andmethod for high strength retention in fiber reinforced thermoplasticcomposite parts or structures that provide advantages over known devicesand methods.

SUMMARY

This need for a molded-in insert and method for high strength retentionin fiber reinforced thermoplastic composite parts or structures issatisfied. As discussed in the below detailed description, embodimentsof the molded-in insert or fitting and method for high strengthretention in fiber reinforced thermoplastic composite parts orstructures and methods may provide significant advantages over existingdevices and methods.

In an embodiment of the disclosure, there is provided a molded-in insertfor high strength retention in a fiber reinforced thermoplasticcomposite structure. The molded-in insert comprises a cylindrical bodyand at least one circumferential groove formed in the cylindrical body.The groove has a substantially concave configuration, has a grooveradius of 0.025 inch or greater, and has a groove radius greater than orequal to a groove depth.

In another embodiment of the disclosure, there is provided a compositepart with a molded-in insert. The composite part comprises a fiberreinforced thermoplastic composite structure comprised of a fiberreinforced thermoplastic composite material. The composite part furthercomprises a molded-in insert secured in the fiber reinforcedthermoplastic composite structure. The molded-in insert comprises acylindrical body and at least one circumferential groove formed in thecylindrical body. The groove has a substantially concave configuration,has a groove radius of 0.025 inch or greater, and has a groove radiusgreater than or equal to a groove depth.

In another embodiment of the disclosure, there is provided a method ofretaining a molded-in insert in a fiber reinforced thermoplasticcomposite material and forming a high strength mechanical lockingmechanism. The method comprises fixing a molded-in insert in a moldcavity. The molded-in insert comprises a cylindrical body and at leastone circumferential groove formed in the cylindrical body. The groovehas a substantially concave configuration, has a groove radius of 0.025inch or greater, and has a groove radius greater than or equal to agroove depth. The method further comprises introducing a fiberreinforced thermoplastic composite material into the mold cavity andaround the molded-in insert. The method further comprises enclosing themold cavity. The method further comprises heating and compressing thefiber reinforced thermoplastic composite material in the mold cavity toconsolidate the fiber reinforced thermoplastic composite material aroundthe molded-in insert, such that reinforcing fibers from the fiberreinforced thermoplastic composite material flow into and fully fill theat least one circumferential groove in order to form a high strengthmechanical locking mechanism that retains the molded-in insert in placein the fiber reinforced thermoplastic composite material and forms aconsolidated fiber reinforced thermoplastic composite structure with themolded-in insert. The method further comprises cooling the consolidatedfiber reinforced thermoplastic composite structure with the molded-ininsert. The method further comprises removing the consolidated fiberreinforced thermoplastic composite structure with the molded-in insertfrom the mold cavity

The features, functions, and advantages that have been discussed can beachieved independently in various embodiments of the disclosure or maybe combined in yet other embodiments further details of which can beseen with reference to the following description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The disclosure can be better understood with reference to the followingdetailed description taken in conjunction with the accompanying drawingswhich illustrate preferred and exemplary embodiments, but which are notnecessarily drawn to scale, wherein:

FIG. 1 is an illustration of a perspective view of an aircraft which mayincorporate one or more advantageous embodiments of a molded-in insertof the disclosure;

FIG. 2A is an illustration of a front perspective view of a knownmolded-in insert with knurled surfaces;

FIG. 2B is an illustration of a front perspective view of a knownmolded-in threaded insert with knurled surfaces;

FIG. 3 is an illustration of a cross-sectional top view of a knownmolded-in insert with a knurled surface after being compression moldedin place in a carbon fiber reinforced thermoplastic composite part;

FIG. 4 is an illustration of a cross-sectional side view of a knownmolded-in insert having a groove with sharp edges and sharp internalcorners molded in place in a carbon fiber reinforced thermoplasticcomposite part;

FIG. 5A is an illustration of a cross-sectional side view showing voidareas of incomplete consolidation;

FIG. 5B is an illustration of a close-up view of the circled portion 5Bof FIG. 5A showing the void areas of incomplete consolidation;

FIG. 6 is an illustration of a front perspective view of one of theembodiments of a molded-in insert of the disclosure having an exteriorcircumferential groove;

FIG. 7 is an illustration of a bottom perspective view of another one ofthe embodiments of a molded-in insert of the disclosure having internalthreads and an exterior circumferential groove;

FIG. 8 is an illustration of a front perspective view of yet another oneof the embodiments of a molded-in insert of the disclosure having twoexterior circumferential grooves;

FIG. 9 is an illustration of a front view of one of the embodiments of amolded-in insert of the disclosure showing groove parameters;

FIG. 10 is an illustration of a top perspective view of one of theembodiments of a molded-in insert of the disclosure having an exteriorcircumferential groove and molded in place in a fiber reinforcedthermoplastic composite structure;

FIG. 11 is an illustration of a cross-sectional top view of themolded-in insert of FIG. 6 molded in place in a fiber reinforcedthermoplastic composite structure and showing full filling of anexterior circumferential groove with reinforcing fibers from fiberreinforced thermoplastic composite material;

FIG. 12 is an illustration of a cross-sectional top view of themolded-in insert of FIG. 8 molded in place in a fiber reinforcedthermoplastic composite structure and showing full filling of twoexterior circumferential grooves with reinforcing fibers from fiberreinforced thermoplastic composite material;

FIG. 13A is an illustration of a top perspective view of one of theembodiments of molded-in inserts of the disclosure molded in place in afiber reinforced thermoplastic composite pinned joint structure;

FIG. 13B is an illustration of a side perspective view of a fiberreinforced thermoplastic fitting portion of the fiber reinforcedthermoplastic composite pinned joint structure with molded-in inserts ofFIG. 13A;

FIG. 14 is an illustration of a bottom perspective view of yet anotherone of the embodiments of a molded-in insert of the disclosure having aninterior circumferential groove and molded in place with a cylindricalfiber reinforced thermoplastic composite structure;

FIG. 15A is an illustration of a front perspective view of yet anotherone of the embodiments of a molded-in insert of the disclosure having anexterior circumferential groove and molded in place in a block-shapedfiber reinforced thermoplastic composite structure;

FIG. 15B is an illustration of a side view of the molded-in insertmolded in place in the block-shaped fiber reinforced thermoplasticcomposite structure of FIG. 15A;

FIG. 16A is an illustration of a front perspective view of yet anotherone of the embodiments of a molded-in insert of the disclosure havingtwo interior circumferential grooves;

FIG. 16B is an illustration of a cross-sectional view taken along lines16B-16B of FIG. 16A;

FIG. 17 is an illustration of a front perspective view of yet anotherone of the embodiments of a molded-in insert of the disclosure having anexterior circumferential groove where the molded-in insert is solid withno central opening;

FIG. 18A is an illustration of a front perspective view of yet anotherone of the embodiments of a molded-in insert of the disclosure having aninterior circumferential groove and an exterior circumferential groove;

FIG. 18B is an illustration of a cross-sectional view taken along lines18B-18B of FIG. 18A;

FIG. 19 is an illustration of a functional block diagram of one of theembodiments of a composite part having one of the embodiments of amolded-in insert of the disclosure;

FIG. 20 is a flow diagram illustrating an exemplary embodiment of amethod of the disclosure;

FIG. 21A is a schematic illustration of a front view of split moldapparatus in an open position having a fiber reinforced thermoplasticcomposite material and one of the embodiments of molded-in inserts ofthe disclosure prior to undergoing compression molding;

FIG. 21B is a schematic illustration of a front view of the split moldapparatus of FIG. 21A in a closed position where the fiber reinforcedthermoplastic composite material and molded-in inserts are compressedand consolidated during compression molding;

FIG. 21C is a schematic illustration of a front view of the split moldapparatus of FIG. 21A in an open position showing a consolidated fiberreinforced thermoplastic composite structure with molded-in insertsafter compression molding; and,

FIG. 22 is an illustration of a cross-sectional view of an internalsecondary structure of an aircraft which may incorporate one or moreadvantageous embodiments of a molded-in insert of the disclosure.

DETAILED DESCRIPTION

Disclosed embodiments will now be described more fully hereinafter withreference to the accompanying drawings, in which some, but not all ofthe disclosed embodiments are shown. Indeed, several differentembodiments may be provided and should not be construed as limited tothe embodiments set forth herein. Rather, these embodiments are providedso that this disclosure will be thorough and complete and will fullyconvey the scope of the disclosure to those skilled in the art.

Now referring to the Figures, FIG. 1 is an illustration of a perspectiveview of an exemplary aircraft 10 that may be made from one or morecomposite parts 102 incorporating one or more advantageous embodimentsof a molded-in insert 100 (or embodiments of molded-in inserts 100 a-100h as shown in FIGS. 6-18B) of the disclosure. As shown in FIG. 1, theaircraft 10 comprises a fuselage 12, a nose 14, a cockpit 16, wings 18operatively coupled to the fuselage 12, one or more propulsion units 20,a tail vertical stabilizer 22, and one or more tail horizontalstabilizers 24. The aircraft 10 may be made from composite and/ormetallic materials that may be used on such portions of the aircraft 10,including but not limited to, the fuselage 12, the nose 14, the wings18, the tail vertical stabilizer 22, and the one or more tail horizontalstabilizers 24. In addition, one or more advantageous embodiments of themolded-in insert 100 (or embodiments of molded-in inserts 100 a-100 h asshown in FIGS. 6-18B) of the disclosure may be used in internalsecondary structures within the aircraft 10. FIG. 22 is an illustrationof a cross-sectional view of an internal secondary structure 70 having aframe 72, outboard storage bins 74, center storage bins 76, interiorpanels 78, and fittings 80. The fittings 80 may be equipped with themolded-in inserts 100 (or embodiments of molded-in inserts 100 a-100 has shown in FIGS. 6-18B) of the disclosure.

Although the aircraft 10 shown in FIG. 1 is generally representative ofa commercial passenger aircraft, the molded-in insert 100 as disclosedherein, may also be employed in other types of aircraft. Morespecifically, the teachings of the disclosed embodiments may be appliedto other passenger aircraft, cargo aircraft, military aircraft,rotorcraft, and other types of aircraft or aerial vehicles, as well asaerospace vehicles, satellites, space launch vehicles, rockets, andother aerospace vehicles. It may also be appreciated that embodiments ofdevices, methods, and systems in accordance with the disclosure may beutilized in other transport vehicles, such as boats and otherwatercraft, trains, automobiles, trucks, buses, or other suitabletransport vehicles. It may further be appreciated that embodiments ofdevices, methods, and systems in accordance with the disclosure may beused in various structures assembled from separate links or pieces, suchas scaffolding, fabric shelters, truss structures, bridges, or othersuitable architectural structures. If the structural fittings and/orlinks are made from a composite material, one or more advantageousembodiments of the molded-in insert 100 (or embodiments of molded-ininserts 100 a-100 h as shown in FIGS. 6-18B) of the disclosure may beused in such structural fittings and/or links where the structure ispinned or connected together.

In one embodiment of the disclosure, there is provided a molded-ininsert 100 for high strength retention in a fiber reinforcedthermoplastic composite structure 130 (see FIG. 10), which may be usedin a composite part 102 (see FIG. 1). FIGS. 6-19 show variousembodiments of the molded-in insert 100, 100 a-100 h. FIG. 6 is anillustration of a front perspective view of one of the embodiments of amolded-in insert 100 a. As shown in FIG. 6, the molded-in insert 100 acomprises a cylindrical body 104. The cylindrical body 104 has anexterior surface 106, an interior surface 108, a first end 112, and asecond end 114. The cylindrical body 104 further comprises a firstcircumferential substantially flat surface 110 a at the second end 114and a second circumferential substantially flat surface 110 b at thefirst end 112. The molded-in insert 100 a further comprises a centralopening 116 for receiving a fastener element 154 (see FIG. 13A), such asa structural pin 156 (see FIG. 13A).

As shown in FIG. 6, the molded-in insert 100 a further comprises atleast one circumferential groove 120 formed in the cylindrical body 104.The circumferential groove 120 preferably has a substantially concaveconfiguration 122 and is preferably shallow in depth. As shown in FIG.6, the molded-in insert 100 a has a single circumferential groove 120formed in the exterior surface 106 of the cylindrical body 104, and themolded-in insert 100 a has an unflanged design. However, the molded-ininsert 100 a or other embodiments of the molded-in insert may have aflanged design as well (see FIG. 7). The circumferential groove 120 maybe formed in the exterior surface 106 of the cylindrical body 104 and/orin the interior surface 108 of the cylindrical body 104 (see FIG. 14) bya known machining process. The circumferential groove 120 may have asurface 170 that may be treated with a surface preparation treatment,discussed below, to promote bonding of a fiber reinforced thermoplasticcomposite material 132 (see FIG. 11) to the surface 170 of the at leastone circumferential groove 120. FIG. 9 is an illustration of a frontview of the molded-in insert 100 a showing various parameters of thecircumferential groove 120. As shown in FIG. 9, the circumferentialgroove 120 has a groove radius 124, a groove depth 126, and a groovewidth 128. Preferably, the groove radius 124 has a length measurement of0.025 inch or greater and preferably, the groove radius 124 is constantor near constant. Preferably, the groove radius 124 is greater in lengththan or equal to the groove depth 126. Preferably, the groove width 128is greater in length than the groove depth 126.

The molded-in insert 100, 100 a-100 h (see FIGS. 6-19) is preferablymade of a machinable material. The machinable material may comprise ametal material such as aluminum, steel, titanium, brass, bronze, oranother suitable metal material. The machinable material may furthercomprise a ceramic material, such as alumina, beryllium oxide, siliconcarbide, silicon nitride, or another suitable ceramic material. Themachinable material may further comprise a composite material such asfilled or unfilled epoxy, phenolic, thermoplastic, urethane,polycarbonate, or another suitable composite material.

FIG. 7 is an illustration of a bottom perspective view of another one ofthe embodiments of a molded-in insert 100 b of the disclosure havinginternal threads 118 formed in the interior surface 108 of thecylindrical body 104 and having a flange 119 extending from first end112. The molded-in insert 100 b comprises the cylindrical body 104having the exterior surface 106, the interior surface 108, the first end112, the second end 114, the first and second circumferentialsubstantially flat surfaces 110 a, 110 b, and the central opening 116.The molded-in insert 100 b further comprises a single circumferentialgroove 120 having the substantially concave configuration 122 and beingshallow in depth. As shown in FIG. 7, the circumferential groove 120 isformed in the exterior surface 106 of the cylindrical body 104.

FIG. 8 is an illustration of a front perspective view of yet another oneof the embodiments of a molded-in insert 100 c of the disclosure havingtwo circumferential grooves 120 formed in the exterior surface 106 ofthe cylindrical body 104. As shown in FIG. 8, the molded-in insert 100 ccomprises the cylindrical body 104 having the exterior surface 106, theinterior surface 108, the first end 112, the second end 114, first andsecond circumferential substantially flat surfaces 110 a, 110 b, and thecentral opening 116. In this embodiment, the molded-in insert 100 cfurther comprises a third circumferential substantially flat surface 110c on a central portion 113 of the cylindrical body 104. The molded-ininsert 100 c further comprises two circumferential grooves 120 eachhaving substantially concave configurations 122 that are formed in theexterior surface 106 of the cylindrical body 104. The twocircumferential grooves 120 are preferably shallow in depth. Thecircumferential groove 120 may have a surface 170 that may be treatedwith a surface preparation treatment, discussed below, to promotebonding of a fiber reinforced thermoplastic composite material 132 (seeFIG. 11) to the surface 170 of the at least one circumferential groove120. The molded-in insert 100 c has an unflanged design. However, themolded-in insert 100 c or other embodiments of the molded-in insert mayhave a flanged design as well (see FIG. 7).

FIG. 14 is an illustration of a bottom perspective view of another oneof the embodiments of a molded-in insert 100 d of the disclosure havinga circumferential groove 120 formed in the interior surface 108 of thecylindrical body 104. FIG. 14 shows the molded-in insert 100 d molded inplace with a cylindrical fiber reinforced thermoplastic compositestructure 140. As shown in FIG. 14, the molded-in insert 100 d comprisesthe cylindrical body 104 having the exterior surface 106, the interiorsurface 108, the first end 112, the second end 114, first and secondcircumferential substantially flat surfaces 110 a, 110 b, and thecentral opening 116. In this embodiment, the exterior surface 106 issmooth and the molded-in insert 100 d comprises a circumferential groove120 having a substantially concave configuration 122 formed in theinterior surface 108 of the cylindrical body 104. Further, in thisembodiment, the molded-in insert 100 d has a protruding element 144extending from the first end 112 of the cylindrical body 104. Themolded-in insert 100 d has an unflanged design. However, the molded-ininsert 100 d or other embodiments of the molded-in insert may have aflanged design as well (see FIG. 7).

FIG. 15A is an illustration of a front perspective view of another oneof the embodiments of a molded-in insert 100 e of the disclosure havinga circumferential groove 120 formed in the exterior surface 106 of thecylindrical body 104 and molded in place in a block-shaped fiberreinforced thermoplastic composite structure 142. FIG. 15B is anillustration of a side view of the molded-in insert 100 e molded inplace in the block-shaped fiber reinforced thermoplastic compositestructure 142 of FIG. 15A. As shown in FIGS. 15A-15B, the molded-ininsert 100 e comprises the cylindrical body 104 having the exteriorsurface 106, the interior surface 108 (not shown), the first end 112,the second end 114, first and second circumferential substantially flatsurfaces 110 a, 110 b, and the central opening 116 (not shown). In thisembodiment, the molded-in insert 100 e comprises a circumferentialgroove 120 having a substantially concave configuration 122 formed inthe exterior surface 106 of the cylindrical body 104. Further, in thisembodiment, the molded-in insert 100 e has a protruding element 146extending from the first end 112 of the cylindrical body 104. Themolded-in insert 100 e has an unflanged design. However, the molded-ininsert 100 e or other embodiments of the molded-in insert may have aflanged design as well (see FIG. 7).

FIG. 16A is an illustration of a front perspective view of another oneof the embodiments of a molded-in insert 100 f of the disclosure havingtwo circumferential grooves 120 formed in the interior surface 108 ofthe cylindrical body 104. FIG. 16B is an illustration of across-sectional view taken along lines 16B-16B of FIG. 16A. As shown inFIGS. 16A-16B, the molded-in insert 100 f comprises the cylindrical body104 having the exterior surface 106, the interior surface 108, the firstend 112, the second end 114, the first circumferential substantiallyflat surface 110 a, and the central opening 116. In this embodiment, themolded-in insert 100 f further comprises two circumferential grooves 120each having substantially concave configurations 122 that are formed inthe interior surface 108 of the cylindrical body 104. The molded-ininsert 100 f has an unflanged design. However, the molded-in insert 100f or other embodiments of the molded-in insert may have a flanged designas well (see FIG. 7).

FIG. 17 is an illustration of a front perspective view of another one ofthe embodiments of a molded-in insert 100 g of the disclosure where themolded-in insert 100 g has a solid interior 148 with no central opening116. The molded-in insert 100 g comprises the cylindrical body 104having the exterior surface 106, the first end 112, the second end 114,and the first and second circumferential substantially flat surfaces 110a, 110 b. This embodiment has a solid interior 148 with no centralopening 116. The molded-in insert 100 g further comprises thecircumferential groove 120 having the substantially concaveconfiguration 122 that is formed in the exterior surface 106 of thecylindrical body 104. The molded-in insert 100 g has an unflangeddesign. However, the molded-in insert 100 g or other embodiments of themolded-in insert may have a flanged design as well (see FIG. 7).

FIG. 18A is an illustration of a front perspective view of another oneof the embodiments of a molded-in insert 100 h of the disclosure havinga first circumferential groove 120 a formed in the interior surface 108of the cylindrical body 104 and having a second circumferential groove120 b formed in the exterior surface 106 of the cylindrical body 104.FIG. 18B is an illustration of a cross-sectional view taken along lines18B-18B of FIG. 18A. As shown in FIGS. 18A-18B, the molded-in insert 100h comprises the cylindrical body 104 having the exterior surface 106,the interior surface 108, the first end 112, the second end 114, thefirst circumferential substantially flat surface 110 a, and the centralopening 116. In this embodiment, the molded-in insert 100 h furthercomprises first and second circumferential grooves 120 a, 120 b eachhaving substantially concave configurations 122, where the firstcircumferential groove 120 a is formed in the interior surface 108 ofthe cylindrical body 104, and the second circumferential groove 120 b isformed in the exterior surface 108 of the cylindrical body 104. Themolded-in insert 100 h has an unflanged design. However, the molded-ininsert 100 h or other embodiments of the molded-in insert may have aflanged design as well (see FIG. 7).

Embodiments of the molded-in inserts 100, 100 a-100 h disclosed hereinbut are not limited to these exemplary embodiments. Embodiments of themolded-in inserts 100, 100 a-100 h may also have more than twocircumferential grooves 120 that may be formed in the exterior surface106 of the cylindrical body 104, that may be formed in the interiorsurface 108 of the cylindrical body 104, or that may be formed in boththe exterior surface 106 and the interior surface 108 of the cylindricalbody 104.

FIG. 10 is an illustration of a top perspective view of one of theembodiments of the molded-in insert 100 a having central opening 116.The molded-in insert 100 a, as shown in FIG. 10, is molded in place in afiber reinforced thermoplastic composite structure 130.

FIG. 11 is an illustration of a cross-sectional top view of a first half101 a and a second half 101 b of the molded-in insert 100 a of FIG. 6which is molded in place in the fiber reinforced thermoplastic compositestructure 130. The central opening 116 between the first half 101 a andthe second half 101 b of the molded-in insert 100 a is shown in FIG. 11as smaller than its actual size, and the first half 101 a and the secondhalf 101 b are shown closer together in order to show the reinforcingfibers 134 fully or completely filling the circumferential groove 120 inthe first half 101 a and in the second half 101 b of the molded-ininsert 100 a. FIG. 11 shows the fiber reinforced thermoplastic compositestructure 130 which comprises fiber reinforced thermoplastic compositematerial 132 having reinforcing fibers 134 in a resin matrix 136. Thereinforcing fibers 134 may be made of a material comprising graphite,glass, carbon, boron, ceramics, aramids, polyolefins, polyethylenes,polymers, or other suitable materials. The resin matrix 136 may be madeof a resin material comprising thermoplastic resins such as polyamides,polyolefins and fluoropolymers; thermosetting resins such as epoxies andpolyesters; hybrid polymer resins with properties of both thermosettingresins and thermoplastic resins; or other suitable resin materials.Preferably, when the molded-in insert 100 a (or the molded-in inserts100, 100 b-100 h) is molded in the fiber reinforced thermoplasticcomposite structure 130, the reinforcing fibers 134 from the fiberreinforced thermoplastic composite material 132 flow into and fully orcompletely fill the circumferential groove 120 and form a high strengthmechanical locking mechanism 138 that secures the molded-in insert 100 ain place in the fiber reinforced thermoplastic composite structure 130.The molded-in insert 100 a (or the molded-in inserts 100, 100 b-100 h)may be molded in the fiber reinforced thermoplastic composite structure130 via a molding process comprising compression molding, resin transfermolding, injection molding, blow molding, transfer molding, reactioninjection molding, casting, investment casting, or another suitablemolding process.

FIG. 12 is an illustration of a cross-sectional top view of themolded-in insert 100 c of FIG. 8 which is molded in place in a fiberreinforced thermoplastic composite structure 130 and which shows fullfilling of two exterior circumferential grooves 120 with reinforcingfibers 134 from fiber reinforced thermoplastic composite material 132.FIG. 12 shows a cross-sectional top view of a first half 103 a and asecond half 103 b of the molded-in insert 100 c of FIG. 8 where themolded-in insert 100 c is molded in place in the fiber reinforcedthermoplastic composite structure 130. The central opening 116 betweenthe first half 103 a and the second half 103 b of the molded-in insert100 c is shown in FIG. 12 as smaller than its actual size, and the firsthalf 103 a and the second half 103 b are shown closer together in orderto show the reinforcing fibers 134 fully or completely filling thecircumferential grooves 120 in both the first half 103 a and the secondhalf 103 b of the molded-in insert 100 c. FIG. 12 shows the fiberreinforced thermoplastic composite structure 130 which preferablycomprises fiber reinforced thermoplastic composite material 132 havingreinforcing fibers 134 in a resin matrix 136. Preferably, when themolded-in insert 100 c is molded in the fiber reinforced thermoplasticcomposite structure 130, the reinforcing fibers 134 from the fiberreinforced thermoplastic composite material 132 flow into and fully orcompletely fill the circumferential grooves 120 and form a high strengthmechanical locking mechanism 138 that secures the molded-in insert 100 cin place in the fiber reinforced thermoplastic composite structure 130.The molded-in insert 100 c may be molded in the fiber reinforcedthermoplastic composite structure 130 via a molding process comprisingcompression molding, resin transfer molding, injection molding, blowmolding, transfer molding, reaction injection molding, casting,investment casting, or another suitable molding process.

Preferably, the molded-in inserts 100, 100 a-100 h disclosed herein aremolded in the fiber reinforced thermoplastic composite structure 130 viacompression molding. Compression molding is particularly suitable formolding large composite structures and parts, such as large flat orcurved fiber reinforced thermoplastic composite structures and parts,for example, wings 18 and fuselage 12 of aircraft 10 (see FIG. 1). FIGS.21A-21C show an exemplary split mold apparatus 172 that may be used in acompression molding process for molding the molded-in inserts 100 or 100a-100 h disclosed herein in the fiber reinforced thermoplastic compositestructure 130.

FIG. 21A is a schematic illustration of a front view of the split moldapparatus 172 holding a fiber reinforced thermoplastic compositematerial 132 and one of the embodiments of molded-in inserts 100 a ofthe disclosure prior to undergoing compression molding. FIG. 21A showsthe split mold apparatus 172 in an open position 173. As shown in FIG.21A, the split mold apparatus 172 preferably comprises a male portion174 and a female portion 176. The male portion 174 may be attached to anupper platen 178 which, in turn, may be attached to a hydraulic ramelement 180. The hydraulic ram element 180 moves the male portion 174with respect to the female portion 176. The female portion 176preferably has a mold cavity 182, and the female portion 176 may beattached to a lower platen 184. An ejector pin 186 may be positionedthrough the lower platen 184 and through the female portion 176 and ispreferably in contact with a molding material 188. The molding material188 may comprise the fiber reinforced thermoplastic composite material132 disclosed herein or another suitable molding material, and themolding material 188 may be introduced or placed into the mold cavity182. The molding material 188 may be in the form of choppedpre-impregnated tape, dry, unmelted pellets, pre-formed sheets, viscousmasses, or another suitable form.

As shown in FIG. 21A, one or more molded-in inserts 100 a (see FIG. 6)(or molded-in inserts 100 or 100 b-100 h disclosed herein) may be loadedinto the mold cavity 182 and trapped by features machined into themolded-in insert itself or fixed or held in place mechanically with oneor more pins 190 for non-threaded molded-in inserts. Alternatively, forthreaded molded-in inserts (see FIG. 7), the molded-in insert may befixed or held in place with a suitable fastener device (not shown). Themold cavity 182 and female portion 176 may be preheated prior to themolding material 188 being placed into the mold cavity 182.Alternatively, the mold cavity 182 and the molding material 188 may beheated once the molding material 188 is placed into the mold cavity 182.Similarly, the male portion 174 may be preheated prior to the moldingmaterial 188 being placed into the mold cavity 182. Alternatively, themale portion 174 may be heated once the molding material 188 is placedinto the mold cavity 182. Finally, the molding material 188 may bepreheated prior to being placed into the mold cavity 182 and thenfurther heated while in the mold cavity 182. Alternatively, the moldingmaterial 188 may be heated while in the mold cavity 182. The mold cavity182, the female portion 176, and the male portion 174 may be preheatedor heated with heat from a heat source 192 connected to heating/coolingchannels 194 formed in the mold cavity 182, female portion 176, and maleportion 174. After the mold material 188 is effectively heated to apliable state in the mold cavity 182, the split mold apparatus 172 ispreferably closed.

FIG. 21B is a schematic illustration of a front view of the split moldapparatus 172 of FIG. 21A where the fiber reinforced thermoplasticcomposite material 132 and molded-in inserts 100 a are compressed andconsolidated during the compression molding process. FIG. 21B shows thesplit mold apparatus 172 in a closed position 195. During compressionmolding process, the hydraulic ram element 180 lowers the male portion174 of the split mold apparatus 172 onto the female portion 176 andcloses the split mold apparatus 172 so as to enclose the mold cavity182. The hydraulic ram element 180 and the male portion 174 apply aneffective pressure to the molding material 188 within the mold cavity182 in order to compress and force the molding material 188, such as thefiber reinforced thermoplastic composite material 132, into contact withall or substantially all internal mold areas 196 (see FIG. 21A) withinthe mold cavity 182 in order to fill the mold cavity 182. During thecompression molding process, the resin matrix 136 of the fiberreinforced thermoplastic composite material 132 preferably encapsulatesthe one or more molded-in inserts 100 a (or molded-in inserts 100 or 100b-100 h disclosed herein) in order to consolidate the fiber reinforcedthermoplastic composite material 132 around the one or more molded-ininserts 100 a (or molded-in inserts 100 or 100 b-100 h disclosed herein)to form the fiber reinforced thermoplastic composite structure 130 withone or more molded-in inserts 100 a (or molded-in inserts 100 or 100b-100 h disclosed herein). In FIG. 21B, the molding material 188, suchas the fiber reinforced thermoplastic composite material 132, is shownas having flowed throughout the mold cavity 182 to form the fiberreinforced thermoplastic composite structure 130 with one or moremolded-in inserts 100 a (or 100 or 100 b-100 h).

When the one or more molded-in inserts 100 a (or molded-in inserts 100or 100 b-100 h disclosed herein) are molded in the fiber reinforcedthermoplastic composite structure 130, the reinforcing fibers 134 fromthe fiber reinforced thermoplastic composite material 132 flow into andfully or completely fill the circumferential grooves 120 and form a highstrength mechanical locking mechanism 138 (see FIG. 11) that retains orsecures the one or more molded-in inserts 100 a (or molded-in inserts100 or 100 b-100 h disclosed herein) in place in the fiber reinforcedthermoplastic composite material 132 to form the consolidated or moldedfiber reinforced thermoplastic composite structure 130 with the one ormore molded-in inserts 100 a (or molded-in inserts 100 or 100 b-100 hdisclosed herein). The molding material 188 may be heated duringmolding, and heat and pressure may be applied for an effective period oftime. For thermoplastic molding material, effective heat and pressureare applied for a period of time of only as long as it takes for thethermoplastic molding material to fill the mold cavity 182. Forthermoset plastic molding material, effective heat and pressure may beapplied for a period of time until the thermoset plastic moldingmaterial cures. Preferably, the pressure used during such compressionmolding process, as disclosed herein, may be in a range of from about1000 psi (pounds per square inch) to about 5000 psi, and morepreferably, in a range of from about 4000 psi to about 5000 psi.Preferably, the temperature used during such compression moldingprocess, as disclosed herein, may be in a range of from about 600degrees Fahrenheit to about 700 degrees Fahrenheit for thermoplasticmolding materials. After the molding material 188 cures, theencapsulated or consolidated one or more molded-in inserts 100 a (ormolded-in inserts 100 or 100 b-100 h disclosed herein) within the fiberreinforced thermoplastic composite structure 130, as well as the moldcavity 182, female portion 176, and male portion 174, may be cooled downon their own via forced convection, or alternatively, may be cooled downwith any suitable active cooling process such as from a cooling source198 which may be connected to heating/cooling channels 194 formed in themold cavity 182. Preferably, after the consolidated fiber reinforcedthermoplastic composite structure 130 with the one or more molded-ininserts 100 a (or molded-in inserts 100 or 100 b-100 h disclosed herein)has sufficiently cooled for an effective period of time, theconsolidated fiber reinforced thermoplastic composite structure 130 withthe one or more molded-in inserts 100 a (or molded-in inserts 100 or 100b-100 h disclosed herein) is removed from the mold cavity 182. The splitmold apparatus 172 may be opened by using the hydraulic ram element 180to raise the male portion 174 of the split mold apparatus 172 away fromthe female portion 176.

FIG. 21C is a schematic illustration of a front view of the split moldapparatus 172 of FIG. 21A showing the consolidated fiber reinforcedthermoplastic composite structure 130 and molded-in inserts 100 a afterthe compression molding process. FIG. 21C shows the split mold apparatus172 in the open position 173 and the molded or consolidated fiberreinforced thermoplastic composite structure 130 with the one or moremolded-in inserts 100 a (or molded-in inserts 100 or 100 b-100 hdisclosed herein). The ejector pin 186 may be used to push upwardly onthe molded or consolidated fiber reinforced thermoplastic compositestructure 130 with the one or more molded-in inserts 100 a (or molded-ininserts 100 or 100 b-100 h disclosed herein) to remove it from the moldcavity 182. The one or more pins 190 or fastener devices (not shown) maybe removed from the mold cavity 182 leaving the encapsulated orconsolidated fiber reinforced thermoplastic composite structure 130 withthe one or more molded-in inserts 100 a (or molded-in inserts 100 or 100b-100 h disclosed herein).

FIG. 13A is an illustration of a top perspective view of one of theembodiments of the molded-in inserts 100 a of the disclosure which ismolded in place in a fiber reinforced thermoplastic composite pinnedjoint structure 150 for use in an aircraft 10 (see FIG. 1). FIG. 13B isan illustration of a side perspective view of a fiber reinforcedthermoplastic fitting portion 152 of the fiber reinforced thermoplasticcomposite pinned joint structure 150 with molded-in inserts 100 a ofFIG. 13A. FIG. 13B shows the molded-in inserts 100 a molded in place andshows the central opening 116 of the molded-in inserts 100 a designed toreceived a fastener element 154 (see FIG. 13A), such as a structural pin156 (see FIG. 13A). As shown in FIG. 13A, the fiber reinforcedthermoplastic fitting portions 152 may be attached to a composite panelstructure 158, a tie-rod 160, and/or a frame fitting 162.

In another embodiment of the disclosure, there is provided a compositepart 102 having one of the embodiments of a molded-in insert 100 (ormolded-in inserts 100 a-100 h disclosed herein) of the disclosure. FIG.19 is an illustration of a functional block diagram of one of theembodiments of the composite part 102 having one of the embodiments of amolded-in insert 100. The composite part 102 may preferably be used in atransport vehicle such as an aircraft 10 (see FIG. 1), an aerospacevehicle, a space launch vehicle, a rocket, a satellite, a rotorcraft, awatercraft, a boat, a train, an automobile, a truck, a bus, or anothersuitable transport vehicle. As shown in FIG. 19, the composite part 102comprises a fiber reinforced thermoplastic composite structure 130. Thefiber reinforced thermoplastic composite structure 130 comprises fiberreinforced thermoplastic composite material 132 having reinforcingfibers 134 in a resin matrix 136. The composite part 102 furthercomprises a molded-in insert 100 secured in and to the fiber reinforcedthermoplastic composite structure 130. The molded-in insert 100, asdiscussed in detail above (or molded-in inserts 100 a-100 h disclosedherein and shown in FIGS. 6-18B), comprises a cylindrical body 104having an exterior surface 106, an interior surface 108, and at leastone circumferential groove 120 formed in the cylindrical body 104. Thecircumferential groove 120 has a substantially concave configuration122. The circumferential groove 120 has a groove radius 124, a groovedepth 126, and groove width 128. Preferably, the groove radius 124 has alength measurement of 0.025 inch or greater. Preferably, the grooveradius 124 is greater in length than or equal to the groove depth 126.Preferably, the groove width 128 is greater in length than the groovedepth 126.

Preferably, when the molded-in insert 100 is molded in the fiberreinforced thermoplastic composite structure 130, reinforcing fibers 134from the fiber reinforced thermoplastic composite material 132 flow intoand fully fill the at least one circumferential groove 120 in order toform a high strength mechanical locking mechanism 138 (see FIG. 19) thatsecures the molded-in insert 100 in place in and to the fiber reinforcedthermoplastic composite structure 130. The molded-in insert 100 may bemolded in the fiber reinforced thermoplastic composite structure 130 viaa molding process comprising compression molding, resin transfermolding, injection molding, blow molding, transfer molding, reactioninjection molding, casting, investment casting, or another suitablemolding process. As discussed above, the molded-in insert 100 ispreferably made of a machinable material. The machinable material maycomprise a metal material such as aluminum, stainless steel, titanium,brass, bronze, or another suitable metal material. The machinablematerial may further comprise a ceramic material, such as alumina,beryllium oxide, silicon carbide, silicon nitride, or another suitableceramic material. The machinable material may further comprise acomposite material such as filled or unfilled epoxy, phenolic,thermoplastic, urethane, polycarbonate, or another suitable compositematerial.

In one embodiment, as shown in FIG. 6, the at least one circumferentialgroove 120 may be formed in the exterior surface 106 of the cylindricalbody 104. In another embodiment, as shown in FIG. 8, the cylindricalbody 104 has two circumferential grooves 120 formed in the exteriorsurface 106 of the cylindrical body 104. In another embodiment, as shownin FIG. 14 , the at least one circumferential groove 120 may be formedin the interior surface 108 of the cylindrical body 104. In anotherembodiment, as shown in FIGS. 16A-16B, the cylindrical body 104 has twocircumferential grooves 120 formed in the interior surface 108 of thecylindrical body 104. In another embodiment, as shown in FIGS. 18A-18B,the cylindrical body 104 may have a first circumferential groove 120 aformed in the exterior surface 106 of the cylindrical body 104 and asecond circumferential groove 120 b formed in the interior surface 108of the cylindrical body 104.

In another embodiment of the disclosure, there is provided a method 200of retaining a molded-in insert 100, or one of the embodiments of themolded-in insert 100 a-100 h disclosed herein, in a fiber reinforcedthermoplastic composite material 132 and forming a high strengthmechanical locking mechanism 138 to secure the molded-in insert 100 (ormolded-in inserts 100 or 100 b-100 h disclosed herein) in a fiberreinforced thermoplastic composite structure 130. FIG. 20 is a flowdiagram illustrating an exemplary embodiment of the method 200 of thedisclosure. The method 200 may initially comprise optional step 202 oftreating a surface 170 (see FIGS. 6, 8) of at least one circumferentialgroove 120 of a molded-in insert 100 (or molded-in inserts 100 or 100b-100 h disclosed herein), to promote bonding of the fiber reinforcedthermoplastic composite material 132 (see FIG. 11) to the surface 170 ofthe at least one circumferential groove 120. The treating of the surface170 of the circumferential groove 120 may comprise one or more surfacepreparation treatments such as solvent wiping, abrading, grit blasting,sanding, sandblasting, chemical cleaning, chemical etching, sol geltreatment, primer treatment, adhesive treatment, or another suitablesurface preparation treatment.

The method 200 further comprises step 204 of fixing the molded-in insert100 (or molded-in inserts 100 or 100 b-100 h disclosed herein) in a moldcavity 182 (see FIG. 21A), such as for example, a mold cavity 182 of asplit mold apparatus 172 (see FIG. 21A). As discussed above, themolded-in insert 100 (or molded-in inserts 100 or 100 b-100 h disclosedherein) comprises a cylindrical body 104 (see, for example, FIGS. 6-8and 14-19). The cylindrical body 104 has exterior surface 106, interiorsurface 108, first end 112, and second end 114 (see, for example, FIGS.6-8). The cylindrical body 104 further comprises first circumferentialsubstantially flat surface 110 a at the second end 114 and secondcircumferential substantially flat surface 110 b at the first end 112(see FIGS. 6-7), and may further comprise third circumferentialsubstantially flat surface 110 c (see FIG. 8). The molded-in insert 100(or molded-in inserts 100 or 100 b-100 h disclosed herein) may furthercomprise central opening 116 for receiving a fastener element 154 (seeFIG. 13A), such as structural pin 156 (see FIG. 13A), or may have asolid interior 148 (see FIG. 17).

The molded-in insert 100 (or molded-in inserts 100 or 100 b-100 hdisclosed herein) further comprises at least one circumferential groove120 (see, for example, FIGS. 6-8 and 14-19) formed in the cylindricalbody 104. The circumferential groove 120 preferably has a substantiallyconcave configuration 122 (see, for example, FIGS. 6-8 and 14-19). Asshown in FIG. 9, the circumferential groove 120 has a groove radius 124,a groove depth 126, and groove width 128. Preferably, the groove radius124 has a length measurement of 0.025 inch or greater. Preferably, thegroove radius 124 is greater in length than or equal to the groove depth126. Preferably, the groove width 128 is greater in length than thegroove depth 126. In one embodiment, as shown in FIG. 6, the at leastone circumferential groove 120 may be formed in the exterior surface 106of the cylindrical body 104. In another embodiment, as shown in FIG. 8,the cylindrical body 104 has two circumferential grooves 120 formed inthe exterior surface 106 of the cylindrical body 104. In anotherembodiment, as shown in FIG. 14, the at least one circumferential groove120 may be formed in the interior surface 108 of the cylindrical body104. In another embodiment, as shown in FIGS. 16A-16B, the cylindricalbody 104 has two circumferential grooves 120 formed in the interiorsurface 108 of the cylindrical body 104. In another embodiment, as shownin FIGS. 18A-18B, the cylindrical body 104 may have a firstcircumferential groove 120 a formed in the exterior surface 106 of thecylindrical body 104 and a second circumferential groove 120 b formed inthe interior surface 108 of the cylindrical body 104.

The method 200 further comprises step 206 of introducing the fiberreinforced thermoplastic composite material 132 (see FIG. 11) into themold cavity 182 and around the molded-in insert 100 (or molded-ininserts 100 or 100 b-100 h disclosed herein). The method 200 furthercomprises step 208 of enclosing the mold cavity 182 (see FIGS. 21A-21B).The method 200 further comprises step 210 of heating via a heat source192 (see FIGS. 21A-21C) and compressing, for example, via a hydraulicram element 180 (see FIGS. 21A-21C), the fiber reinforced thermoplasticcomposite material 132 in the mold cavity 182 to consolidate the fiberreinforced thermoplastic composite material 132 around the molded-ininsert 100 (or molded-in inserts 100 or 100 b-100 h disclosed herein),such that reinforcing fibers 134 from the fiber reinforced thermoplasticcomposite material 132 flow into and fully fill the at least onecircumferential groove 120 in order to form a high strength mechanicallocking mechanism 138 (see FIG. 11) that retains the molded-in insert100, or one of the embodiments 100 a-100 h, in place in the fiberreinforced thermoplastic composite material 132 and in order to form aconsolidated fiber reinforced thermoplastic composite structure 130 withthe molded-in insert 100 (or molded-in inserts 100 or 100 b-100 hdisclosed herein).

The method 200 further comprises step 212 of cooling the consolidatedfiber reinforced thermoplastic composite material 132 with molded-ininsert 100 (or molded-in inserts 100 or 100 b-100 h disclosed herein).The cooling step 212 may be conducted via forced convection, oralternatively, with any suitable active cooling process such as from acooling source 198 (see FIGS. 21A-21C) which may be connected toheating/cooling channels 194 (see FIGS. 21A-21C) such as formed in amold cavity 182 (see FIGS. 21A-21C). The molded-in insert 100 (ormolded-in inserts 100 or 100 b-100 h disclosed herein) is preferablyconsolidated with the fiber reinforced thermoplastic composite structure130 via a molding process comprising compression molding, resin transfermolding, injection molding, blow molding, transfer molding, reactioninjection molding, casting, investment casting, or another suitablemolding process. The method 200 further comprises step 214 of removingthe consolidated fiber reinforced thermoplastic composite material 132with molded-in insert 100 (or molded-in inserts 100 or 100 b-100 hdisclosed herein) from the mold cavity 182 of the split mold apparatus172 (see FIG. 21C).

Preferably, the method 200 minimizes or eliminates formation of voidareas 56 (see FIGS. 3, 4) of incomplete consolidation where there is noor minimal reinforcement. In addition, preferably, the method 200minimizes or eliminates the severing or cutting of any of thereinforcing fibers 134 in the fiber reinforced thermoplastic compositematerial 132 by sharp edges 40 (see FIG. 4).

Disclosed embodiments of the molded-in insert 100 or 100 a-100 h andmethod 200 provide molded-in inserts having at least one relativelyshallow, circumferential groove 120 (see FIGS. 6-8 and 14-18B) formolding in place within or to fiber reinforced thermoplastic compositestructures 130 (see FIG. 10) preferably used in composite parts 102 (seeFIG. 1). In addition, disclosed embodiments of the molded-in inserts 100or 100 a-100 h and method 200 provide molded-in inserts having at leastone relatively shallow, circumferential groove 120 and having arelatively large open volume which allow the reinforcing fibers 134 toenter the circumferential groove 120 and completely or substantiallyfill the circumferential groove 120 and to form a high strengthmechanical locking mechanism 138 (see FIG. 11) during the moldingprocess. Such high strength mechanical locking mechanism 138 retains orcaptures the molded-in insert 100 or 100 a-100 h in the fiber reinforcedthermoplastic composite structure 130 in such a way as to develop thefull strength of the surrounding fiber reinforced thermoplasticcomposite material 132 and not just the strength of the resin matrix136.

Disclosed embodiments of the molded-in inserts 100 or 100 a-100 h andmethod 200 may provide full capture strength of the molded-in inserts100 or 100 a-100 h within the fiber reinforced thermoplastic compositestructure 130, may eliminate or minimize the formation of void areas 56(see FIGS. 3, 4) of incomplete consolidation, and may eliminate orminimize the cutting of the reinforcing fibers 134 in the resin matrix136 by sharp edges 40 (see FIG. 4) which may reduce capture strength.Further, disclosed embodiments of the molded-in inserts 100 or 100 a-100h and method 200 may be used to receive mating fasteners, provide robustattachment points for multi-part assemblies, provide load transferpoints, avoid the costs of known post-molding insert or fittinginstallation methods, such as bonding in place, drilling and tapping, orother mechanical capture methods that utilize press-fit inserts orswaged inserts, and reduce final part costs compared to knownpost-molding insert or fitting installation methods which may add, forexample, additional set-up and operating time or adhesive applicationand drying time.

Many modifications and other embodiments of the disclosure will come tomind to one skilled in the art to which this disclosure pertains havingthe benefit of the teachings presented in the foregoing descriptions andthe associated drawings. The embodiments described herein are meant tobe illustrative and are not intended to be limiting or exhaustive.Although specific terms are employed herein, they are used in a genericand descriptive sense only and not for purposes of limitation.

1. A molded-in insert for high strength retention in a fiber reinforcedthermoplastic composite structure, the molded-in insert comprising: acylindrical body; and, at least one circumferential groove formed in thecylindrical body, the groove having a substantially concaveconfiguration, having a groove radius of 0.025 inch or greater, andhaving the groove radius greater than or equal to a groove depth.
 2. Theinsert of claim 1, wherein the at least one circumferential groove has agroove width greater than the groove depth.
 3. The insert of claim 1,wherein when the molded-in insert is molded in a fiber reinforcedthermoplastic composite structure, reinforcing fibers from the fiberreinforced thermoplastic composite structure flow into and fully fillthe at least one circumferential groove in order to form a high strengthmechanical locking mechanism that secures the molded-in insert in placein the fiber reinforced thermoplastic composite structure.
 4. The insertof claim 3, wherein the molded-in insert is molded in the fiberreinforced thermoplastic composite structure via a molding processselected from a group comprising compression molding, resin transfermolding, injection molding, blow molding, transfer molding, reactioninjection molding, casting, and investment casting.
 5. The insert ofclaim 1, wherein the at least one circumferential groove is formed in anexterior surface of the cylindrical body.
 6. The insert of claim 1,wherein the at least one circumferential groove is formed in an interiorsurface of the cylindrical body.
 7. The insert of claim 1, wherein thecylindrical body has two or more circumferential grooves formed in anexterior surface of the cylindrical body.
 8. The insert of claim 1,wherein the cylindrical body has two or more circumferential groovesformed in an interior surface of the cylindrical body.
 9. The insert ofclaim 1, wherein the cylindrical body has a first circumferential grooveformed in an exterior surface of the cylindrical body and a secondcircumferential groove formed in an interior surface of the cylindricalbody.
 10. The insert of claim 1, wherein the molded-in insert is made ofa machinable material selected from a group comprising a metal material,a ceramic material, and a composite material.
 11. A composite part witha molded-in insert, the composite part comprising: a fiber reinforcedthermoplastic composite structure comprised of a fiber reinforcedthermoplastic composite material; a molded-in insert secured in thefiber reinforced thermoplastic composite structure, the molded-in insertcomprising: a cylindrical body; and, at least one circumferential grooveformed in the cylindrical body, the groove having a substantiallyconcave configuration, having a groove radius of 0.025 inch or greater,and having the groove radius greater than or equal to a groove depth.12. The composite part of claim 11, wherein the at least onecircumferential groove has a groove width greater than the groove depth.13. The composite part of claim 11, wherein the at least onecircumferential groove is formed in an exterior surface of thecylindrical body.
 14. The composite part of claim 11, wherein the atleast one circumferential groove is formed in an interior surface of thecylindrical body.
 15. The composite part of claim 11, wherein thecylindrical body has a first circumferential groove formed in anexterior surface of the cylindrical body and a second circumferentialgroove formed in an interior surface of the cylindrical body.
 16. Thecomposite part of claim 11, wherein the composite part is used in atransport vehicle selected from a group comprising an aircraft, anaerospace vehicle, a space launch vehicle, a rocket, a satellite, arotorcraft, a watercraft, a boat, a train, an automobile, a truck, and abus.
 17. A method of retaining a molded-in insert in a fiber reinforcedthermoplastic composite material and forming a high strength mechanicallocking mechanism, the method comprising: fixing a molded-in insert in amold cavity, the insert comprising: a cylindrical body; and, at leastone circumferential groove formed in the cylindrical body, the groovehaving a substantially concave configuration, having a groove radius of0.025 inch or greater, and having the groove radius greater than orequal to a groove depth; introducing a fiber reinforced thermoplasticcomposite material into the mold cavity and around the molded-in insert;enclosing the mold cavity; heating and compressing the fiber reinforcedthermoplastic composite material in the mold cavity to consolidate thefiber reinforced thermoplastic composite material around the molded-ininsert, such that reinforcing fibers from the fiber reinforcedthermoplastic composite material flow into and fully fill the at leastone circumferential groove in order to form a high strength mechanicallocking mechanism that retains the molded-in insert in place in thefiber reinforced thermoplastic composite material and forms aconsolidated fiber reinforced thermoplastic composite structure with themolded-in insert; cooling the consolidated fiber reinforcedthermoplastic composite structure with the molded-in insert; and,removing the consolidated fiber reinforced thermoplastic compositestructure with the molded-in insert from the mold cavity.
 18. The methodof claim 17, further comprising prior to fixing the molded-in insert inthe mold cavity, treating a surface of the at least one circumferentialgroove of the molded-in insert to promote bonding of the fiberreinforced thermoplastic composite material to the surface of the atleast one circumferential groove.
 19. The method of claim 18, whereintreating the surface of the at least one circumferential groovecomprises one or more surface preparation treatments selected from agroup comprising solvent wiping, abrading, grit blasting, sanding,sandblasting, chemical cleaning, chemical etching, sol gel treatment,primer treatment, and adhesive treatment.
 20. The method of claim 17,wherein the molded-in insert is consolidated with the fiber reinforcedthermoplastic composite material via a molding process selected from agroup comprising compression molding, resin transfer molding, injectionmolding, blow molding, transfer molding, reaction injection molding,casting, and investment casting.
 21. The method of claim 17, wherein themethod minimizes or eliminates formation of void areas of noreinforcement and minimizes or eliminates cutting of fibers in the fiberreinforced thermoplastic composite material.
 22. The method of claim 17,wherein the at least one circumferential groove is formed in an exteriorsurface of the cylindrical body.
 23. The method of claim 17, wherein theat least one circumferential groove is formed in an interior surface ofthe cylindrical body.
 24. The method of claim 17, wherein thecylindrical body has a first circumferential groove formed in anexterior surface of the cylindrical body and a second circumferentialgroove formed in an interior surface of the cylindrical body.